Mounting device for stationary blade inner shroud ring of gas turbine

Abstract

The utility model relates to the technical field of gas turbine general assembly, and provides a gas turbine stationary blade inner shroud ring installation device which comprises a placing frame, universal wheels and a top plate, and supporting assemblies are arranged at the front end and the rear end of the bottom of the placing frame. The distance can be automatically adjusted according to the width of the inner shroud ring, and the inner shroud ring can be tightly abutted and fixed, so that the inner shroud ring can be positioned when placed and can be accurately placed on the top of a top plate. Therefore, not only is the stability of the inner shroud ring when the inner shroud ring is buckled up and down guaranteed, but also installation errors caused by placement deviation are avoided. The height of the placing frame in the front-back and left-right directions can be controlled through the adjusting screw rods which are independently adjustable in the four directions, and the unbalance problem between the inner shroud ring and the blades can be rapidly corrected. The height of the inner shroud ring and the height of the blade are kept consistent in all dimensions through flexible adjustment, it is guaranteed that the installation process is conducted safely and smoothly, and the blade is effectively protected against damage.

Description

Technical Field

[0001] This utility model relates to the field of gas turbine assembly technology, and in particular to an installation device for the inner circumference strip of a gas turbine stator blade. Background Technology

[0002] A gas turbine is a type of power machinery that converts the heat energy released from the combustion of fuel inside the machine into power. The stator blade inner shroud plays a crucial role in significantly improving the efficiency, reliability, and lifespan of the gas turbine through structural integration, optimized sealing, aerodynamic guidance, and thermal management. Its design requirements balance material temperature resistance and aerodynamics, making it an indispensable functional component of the gas turbine stator system. However, the inner shroud itself is relatively heavy, and due to its function and close connection to the stator blades, the positional relationship between the inner shroud and the blades is complex. This makes it easy for the blades to be bumped during the installation of the inner shroud, resulting in significant manpower and economic losses. To ensure stable and precise installation of the inner shroud and blade bushings, and to effectively improve installation efficiency and quality, an installation device for the gas turbine stator blade inner shroud is required.

[0003] However, existing gas turbine stator blade inner circumference strip installation devices have many shortcomings. On the one hand, they lack effective limiting and adjustment structures, making it difficult to cope with the large weight of the inner circumference strip itself and the complex relationship between it and the blade position. This leads to the inner circumference strip being prone to misalignment during installation, which in turn can cause it to collide with the blade, resulting in equipment damage and economic losses.

[0004] On the other hand, the installation process often requires multiple people to work together to observe and maintain balance, which results in high labor costs and low operating efficiency, failing to meet the actual needs of high-precision and safe installation. Utility Model Content

[0005] The purpose of this invention is to provide an installation device for the inner circumference strip of a gas turbine stator blade, thereby solving the above-mentioned problems.

[0006] To solve the above-mentioned technical problems, the present invention provides the following technical solution: an installation device for the inner circumference of a gas turbine stator blade, comprising a placement frame, casters and a top plate, with support components provided at the front and rear ends of the bottom of the placement frame, casters installed at the four corners of the bottom of the placement frame, and a top plate fixed to the top of the placement frame, with a limit component provided on the top of the top plate.

[0007] Preferably, the support assembly includes a support sleeve fixed to the front and rear ends of the bottom of the placement frame, an adjusting screw is connected to the internal thread of the support sleeve, and a support base is fixed to the bottom of the adjusting screw.

[0008] Preferably, four sets of support screw sleeves are provided, and the four sets of support screw sleeves are symmetrically distributed at both ends of the center line of the placement frame.

[0009] Preferably, the limiting component includes a support block fixed to the top of the top plate, and a limiting stop block is provided at one end of the two opposing support blocks. A through groove is opened inside the support block, and a connecting rod is provided inside the through groove. One end of the connecting rod is fixedly connected to the limiting stop block, and a spring is provided between the limiting stop block and the support block. The spring is wound around the outside of the connecting rod.

[0010] Preferably, one end of the spring is fixedly connected to the outer wall of the support block, and the other end of the spring is fixedly connected to the outer wall of the limiting block.

[0011] Preferably, a guide block is fixed to the bottom of the limiting block, and the guide block is placed inside the guide groove.

[0012] Preferably, the size of the guide block matches the size of the guide groove, and the guide block can slide inside the guide groove.

[0013] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0014] 1. This utility model provides an installation device for the inner circumference strip of a gas turbine stator blade. Through three sets of self-adjusting limiting components on the top plate, and utilizing the cooperation of springs and limiting blocks, the device automatically adjusts the spacing according to the width of the inner circumference strip and secures it tightly. This effectively solves the positioning problem when placing the inner circumference strip, ensuring its accurate placement on the top of the top plate. This not only ensures the stability of the inner circumference strip when it is fastened vertically, but also avoids installation errors caused by placement misalignment, greatly improving installation accuracy and reliability.

[0015] 2. This utility model provides an installation device for the inner circumference strip of a gas turbine stator blade. Four independently adjustable screws control the height of the mounting frame in the front-back, left-right, and right directions, quickly correcting imbalances between the inner circumference strip and the blade, and eliminating the risk of collisions caused by misalignment. Flexible adjustment ensures that the inner circumference strip and the blade maintain high consistency in all dimensions, guaranteeing a safe and smooth installation process and effectively protecting the blade from damage.

[0016] 3. This utility model provides an installation device for the inner circumference strip of a gas turbine stator blade. The design of this device significantly optimizes the installation process. Previously, at least two people were required to observe and maintain the balance of the inner circumference strip; now, a single person can complete the operation. Its convenient compatibility with a hand-cranked forklift, self-adaptive limit, and adjustment functions greatly reduce manpower input, effectively save labor costs, improve installation efficiency, and reduce the complexity and error rate of manual operation. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention. Figure 1 ;

[0018] Figure 2 This is a partial structural schematic diagram of the present invention;

[0019] Figure 3 This is a schematic diagram of the limiting component structure of this utility model;

[0020] Figure 4 This is a front structural cross-sectional view of the limiting component of this utility model;

[0021] Figure 5 This is a schematic diagram of the disassembled structure of the limiting component and the top plate of this utility model;

[0022] Figure 6 This is a schematic diagram of the overall structure of the present invention. Figure 2 .

[0023] The following are the annotations in the figure: 1. Placement frame; 2. Support screw sleeve; 21. Adjusting screw; 22. Support base; 3. Caster wheel; 4. Top plate; 5. Support block; 51. Limiting block; 52. Connecting rod; 53. Spring; 54. Through groove; 6. Guide block; 61. Guide groove. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] To further understand the content of this utility model, a detailed description of this utility model will be provided in conjunction with the accompanying drawings.

[0026] Combination Figures 1 to 6 As shown, the present invention provides an installation device for the inner circumference strip of a gas turbine stator blade, comprising a placement frame 1, casters 3, and a top plate 4. Support components are provided at the front and rear ends of the bottom of the placement frame 1, casters 3 are installed at the four corners of the bottom of the placement frame 1, and a top plate 4 is fixed to the top of the placement frame 1. A limit component is provided on the top of the top plate 4.

[0027] The support assembly includes a support sleeve 2 fixed to the front and rear ends of the bottom of the placement frame 1. An adjusting screw 21 is connected to the internal thread of the support sleeve 2, and a support base 22 is fixed to the bottom of the adjusting screw 21.

[0028] There are four sets of support screw sleeves 2, which are symmetrically distributed at both ends of the center line of the placement frame 1.

[0029] The limiting component includes a support block 5 fixed to the top of the top plate 4. One end of the two opposing support blocks 5 is provided with a limiting block 51. A through groove 54 is opened inside the support block 5. A connecting rod 52 is provided inside the through groove 54. One end of the connecting rod 52 is fixedly connected to the limiting block 51. A spring 53 is provided between the limiting block 51 and the support block 5. The spring 53 is wrapped around the outside of the connecting rod 52.

[0030] One end of the spring 53 is fixedly connected to the outer wall of the support block 5, and the other end of the spring 53 is fixedly connected to the outer wall of the limiting block 51.

[0031] A guide block 6 is fixed to the bottom of the limiting block 51, and the guide block 6 is placed inside the guide groove 61.

[0032] The size of the guide block 6 matches the size of the guide groove 61, and the guide block 6 can slide inside the guide groove 61.

[0033] Specifically, first place the gas turbine stator blade inner circumference mounting device on the hand-cranked forklift, align the support base 22 with the two brackets of the hand-cranked forklift, and push the support base 22 down by rotating the adjusting screw 21 to lift the caster wheel 3 away from the ground. Use the adjusting screw 21 in conjunction with the support base 22 to support the placement frame 1 and place it on the hand-cranked forklift.

[0034] Two opposing limiting blocks 51 form a set of limiting components. Three sets of limiting components are provided on the top of the top plate 4. The inner circumference belt to be installed is placed above the top plate 4, so that the inner circumference belt is placed between the three sets of limiting components. The outer wall of the inner circumference belt pushes the opposing limiting blocks 51 outward. The limiting blocks 51 drive the connecting rod 52 to slide in the through groove 54. At the same time, the compression spring 53 contracts. The spring 53 uses its own elastic force to push the limiting blocks 51 back to make it press against the side wall of the inner circumference belt. In this way, the limiting treatment of the inner circumference belt can be completed. The limiting of the inner circumference belt can ensure that the inner circumference belt is accurately placed on the top of the top plate 4. Furthermore, the position of the two opposing limiting blocks 51 can be adaptively adjusted according to the width of the inner circumference belt to accommodate the limiting of inner circumference belts of different sizes. Then, the hand-cranked forklift and the gas turbine stationary blade inner circumference belt installation device are pushed directly below the blade to be installed.

[0035] By manually turning the four-way adjusting screws 21, the height of the placement frame 1 in the front-back, left-right and right directions can be adjusted so that the inner circumference strip placed on the top of the top plate 4 is level with the blade in the front-back, left-right and right directions.

[0036] Slowly raise the hand-cranked forklift to ensure the inner circumference of the top plate 4 is perfectly integrated with the blade bushing, completing the installation.

[0037] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0038] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An installation device for the inner circumference strip of a gas turbine stator blade, comprising a mounting frame (1), casters (3), and a top plate (4), characterized in that: The bottom of the placement rack (1) is provided with support components at the front and rear ends. Universal wheels (3) are installed at the four corners of the bottom of the placement rack (1). A top plate (4) is fixed to the top of the placement rack (1). A limit component is provided on the top of the top plate (4).

2. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 1, characterized in that: The support assembly includes a support sleeve (2) fixed to the front and rear ends of the bottom of the placement frame (1). The internal thread of the support sleeve (2) is connected to an adjusting screw (21), and the bottom of the adjusting screw (21) is fixed to a support base (22).

3. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 2, characterized in that: The support screw sleeves (2) are provided in four sets, and the four sets of support screw sleeves (2) are symmetrically distributed at both ends of the center line of the placement frame (1).

4. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 3, characterized in that: The limiting component includes a support block (5) fixed to the top of the top plate (4). One end of the two opposing support blocks (5) is provided with a limiting block (51). A through groove (54) is opened inside the support block (5). A connecting rod (52) is provided inside the through groove (54). One end of the connecting rod (52) is fixedly connected to the limiting block (51). A spring (53) is provided between the limiting block (51) and the support block (5). The spring (53) is wrapped around the outside of the connecting rod (52).

5. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 4, characterized in that: One end of the spring (53) is fixedly connected to the outer wall of the support block (5), and the other end of the spring (53) is fixedly connected to the outer wall of the limiting block (51).

6. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 5, characterized in that: The bottom of the limiting block (51) is fixed with a guide block (6), which is placed inside the guide groove (61).

7. The installation device for the inner circumference strip of a gas turbine stator blade according to claim 6, characterized in that: The size of the guide block (6) matches the size of the guide groove (61), and the guide block (6) can slide inside the guide groove (61).

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